Design methodology and mission assessment of parallel hybrid electric propulsion systems

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dc.contributor.authorGhelani, Raj
dc.contributor.authorRoumeliotis, Ioannis
dc.contributor.authorSaias, Chana Anna
dc.contributor.authorMourouzidis, Christos
dc.contributor.authorPachidis, Vassilios
dc.contributor.authorNorman, Justin
dc.contributor.authorBacic, Marko
dc.date.accessioned2022-09-28T10:40:06Z
dc.date.available2022-09-28T10:40:06Z
dc.date.issued2022-09-16
dc.description.abstractAn integrated engine cycle design methodology and mission assessment for parallel hybrid electric propulsion architectures are presented in this paper. The aircraft case study considered is inspired by Fokker 100, boosted by an electric motor on the low-pressure shaft of the gas turbine. The fuel burn benefits arising from boosting the low-pressure shaft are discussed for two different baseline engine technologies. A three-point engine cycle design method is developed to redesign the engine cycle according to the degree of hybridization. The integrated cycle design and power management optimization method is employed to identify potential fuel burn benefits from hybridization for multiple mission ranges. The sensitivity of these mission results has also been analyzed for different assumptions on the electric powertrain. With 1 MW motor power and a battery pack of 2307 kg, a 3% fuel burn benefit can be obtained by retrofitting the gas turbine for 400 nm range. Optimizing the power management strategy improves this fuel burn benefit by 0.2-0.3%. Redesigning the gas turbine and optimizing the power management strategy, provides a 4.2% fuel benefit on 400 nm. The results suggest that a high hybridization by power, low hybridization by energy, and ranges below 700 nm are the only cases where the redesigned hybrid electric aircraft has benefits in fuel burn and energy consumption relative to the baseline aircraft. Finally, it is found that the percentage of fuel burn benefits from the hybrid electric configuration increases with the improvement in engine technology.en_UK
dc.identifier.citationGhelani RA, Roumeliotis I, Saias CA, et al., (2023) Design methodology and mission assessment of parallel hybrid electric propulsion systems. Journal of Engineering for Gas Turbines and Power, Volume 145, Issue 3, March 2023, Article number 031002, Paper number GTP-22-1416en_UK
dc.identifier.issn0742-4795
dc.identifier.urihttps://doi.org/10.1115/1.4055635
dc.identifier.urihttps://asmedigitalcollection.asme.org/gasturbinespower/article/doi/10.1115/1.4055635/1146249/Design-Methodology-and-Mission-Assessment-of
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/18477
dc.language.isoenen_UK
dc.publisherAmerican Society of Mechanical Engineersen_UK
dc.rightsAttribution 4.0 International*
dc.rights.urihttp://creativecommons.org/licenses/by/4.0/*
dc.subjecthybrid electricen_UK
dc.titleDesign methodology and mission assessment of parallel hybrid electric propulsion systemsen_UK
dc.typeArticleen_UK

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